Film cooling analysis of injection configurations for afterburner aero-engine applications.

Abstract

There is a significant need for thrust augmentation in aircraft for several specific operations, such as combat or take-off from short runways. The additional thrust requirement is achieved by burning extra fuel in the afterburner, which further raises the temperature to 2200K. In order to increase thermal efficiency and power output, the turbine entry temperature of modern gas turbine engines has to be increased considerably. Furthermore, the exposed components in the pathway of the exhaust stream experience a very high temperature. Therefore, to maintain the permissible metal temperature for safe operation, the component under such high thermal loads requires a sophisticated cooling technique. “Film cooling” is one of the most adopted to protect the component which is subjected to hot flue gases.